Abstract:

The purpose of the present paper is to investigate the optimization design of climb trajectory with multiple constraints for an air-breathing supersonic missile, and a trajectory/ramjet optimal design method which is suitable for this kind of aircraft is proposed under the condition that considering multiple constraints and strong coupling of the air-breathing supersonic missile in flight process. The performance of the air-breathing ramjet is analyzed and the law of thrust, static margin and excess coefficient varying with the flight condition is ascertained in climb trajectory. A multi-constraint trajectory optimization model is established with the constraints of ramjet, overload, dynamic pressure and terminal parameters, and a numerical example that minimizes the fuel consumption of the climb trajectory is presented. Numerical simulation results indicate the effectiveness of the proposed method in solving the trajectory optimization design problem with multiple constraints and provide reference for the trajectory planning and guidance law design of the air-breathing supersonic missile.

Key words: Air-breathing supersonic missile, Ramjet, Multiple constraints, Strong coupling, Climb trajectory optimization design